Airworthiness Directives; Piaggio Aviation S.p.A. Airplanes, 90085-90088 [2023-28769]

Download as PDF 90085 Rules and Regulations Federal Register Vol. 88, No. 249 Friday, December 29, 2023 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–1819; Project Identifier MCAI–2023–00052–A; Amendment 39–22630; AD 2023–25–03] RIN 2120–AA64 Airworthiness Directives; Piaggio Aviation S.p.A. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Piaggio Aviation S.p.A. (Piaggio) Model P–180 airplanes. This AD is prompted by a report of corrosion on the various aluminum alloy reinforcements in the horizontal stabilizer (HS) central box caused by a humid environment inside the box from water ingress and/or condensation. This AD requires a onetime detailed inspection of the HS central box for corrosion; an assessment of the corrosion level; and depending on the determination, repetitive detailed inspections of the HS central box for corrosion and the internal composite structure for surface cracks, distortion, and damage; and repair or replacement of the HS assembly. Repair or replacement of the HS assembly is terminating action for the repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 2, 2024. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 2, 2024. ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov under Docket No.FAA– 2023–1819; or in person at Docket Operations between 9 a.m. and 5 p.m., ddrumheller on DSK120RN23PROD with RULES1 SUMMARY: VerDate Sep<11>2014 16:47 Dec 28, 2023 Jkt 262001 Monday through Friday, except Federal holidays. The AD docket contains this final rule, the mandatory continuing airworthiness information (MCAI), any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. Material Incorporated by Reference: • For service information identified in this final rule, contact Piaggio Aviation S.p.A., P180 Customer Support, via Pionieri e Aviatori d’Italia, snc—16154 Genoa, Italy; phone: +39 331 679 74 93; email: technicalsupport@ piaggioaerospace.it. • You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (817) 222–5110. It is also available at regulations.gov under Docket No. FAA–2023–1819. FOR FURTHER INFORMATION CONTACT: Sungmo Cho, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (781) 238– 7241; email: sungmo.d.cho@faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain serial-numbered Piaggio Model P–180 airplanes. The NPRM published in the Federal Register on September 7, 2023 (88 FR 61482). The NPRM was prompted by AD 2023–0007, dated January 13, 2023 (also referred to as the MCAI), issued by the European Union Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union. The MCAI states that an occurrence of corrosion was found inside the HS central box of a Piaggio Model P–180 airplane during scheduled maintenance. A subsequent investigation and inspection of 16 other Piaggio Model P– 180 airplanes of various configurations and ages revealed that corrosion of differing levels of severity was found on various aluminum alloy reinforcements in the HS central box of all the inspected airplanes. The MCAI also states that this corrosion was caused by PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 the formation of a humid environment inside the HS central box, from water ingress and/or condensation. Further investigation revealed that airplanes left in prolonged inactivity or parked outside are more prone to develop corrosion damage. To address the unsafe condition, the MCAI requires a one-time detailed inspection of the HS central box for corrosion, contacting Piaggio for a determination of the corrosion level, and depending on that determination, repetitive detailed inspections of the HS central box for corrosion and the internal composite structure for surface cracks, distortion, and damage; and depending on the results, repair or replacement of the HS assembly. The MCAI states that repair or replacement of the HS assembly is terminating action for the repetitive inspections. In the NPRM, the FAA proposed to require a one-time detailed inspection of the HS central box for corrosion; an assessment of the corrosion level; and depending on the determination, repetitive detailed inspections of the HS central box for corrosion and the internal composite structure for surface cracks, distortion, and damage; and repair or replacement of the HS assembly. Repair or replacement of the HS assembly is terminating action for the repetitive inspections. The FAA is issuing this AD to address corrosion on the various aluminum alloy reinforcements in the HS central box. The unsafe condition, if not addressed, could result in reduced structural integrity of the HS, and loss of control of the airplane. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2023–1819. Discussion of Final Airworthiness Directive Comments The FAA received a comment from one individual commenter. The commenter supported the NPRM and requested a change. The following presents the comment received on the NPRM and the FAA’s response to the comment. Request To Revise Costs of Compliance Section of the NPRM An individual commenter requested that the FAA contact Piaggio for the exact price per unit of replacement E:\FR\FM\29DER1.SGM 29DER1 90086 Federal Register / Vol. 88, No. 249 / Friday, December 29, 2023 / Rules and Regulations parts. The commenter explained that this would provide operators with a more accurate estimate of the NPRM’s economic effect and allow operators to be financially prepared. The FAA disagrees with the commenter’s request because the estimated cost for a replacement HS assembly provided in this final rule is based on a cost estimate from Piaggio. Accordingly, the FAA considers the cost estimates provided in this final rule to be sufficient and the FAA has not changed this AD regarding this issue. Conclusion These products have been approved by the aviation authority of another country and are approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with this State of Design Authority, it has notified the FAA of the unsafe condition described in the MCAI referenced above. The FAA reviewed the relevant data, considered the comment received, and determined that air safety requires adopting this AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. This AD is adopted as proposed in the NPRM. Related Service Information Under 1 CFR Part 51 The FAA reviewed Piaggio Aerospace Service Bulletin 80–0489, Revision 2, dated November 30, 2022 (Piaggio SB 80–0489, Revision 2). This service information specifies procedures for a one-time detailed inspection of the HS central box for corrosion, a report of the inspection results to Piaggio for a determination of the corrosion level, repetitive inspections of the HS central box as needed, and applicable corrective actions. The corrective actions include installation of a serviceable HS assembly, which is terminating action for the repetitive inspections. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in ADDRESSES. Differences Between This AD and the MCAI The MCAI requires contacting the manufacturer for a determination of the corrosion level if any corrosion is found during the initial inspection of the HS central box, and if it is determined that level 2 or 3 corrosion is present, having the manufacturer provide the threshold and intervals for doing repetitive inspections of the HS central box. This AD requires contacting either the FAA, EASA, or Piaggio’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. Although Piaggio SB 80–0489, Revision 2, specifies to record the image of the location of corroded areas, this AD does not require that action. Costs of Compliance The FAA estimates that this AD affects 102 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Initial inspection of HS central box for corrosion 6 work-hours × $85 per hour = $510 ................. $0 $510 $52,020 ON-CONDITION COSTS Action Labor cost Repetitive inspections of HS central box for corrosion. Repetitive inspections for surface cracks, distortion, and damage. Replace HS assembly .............................. 6 work-hours × $85 per hour = $510, per inspection cycle. 6 work-hours × $85 per hour = $510 ....... $0 $510, per inspection cycle. 0 $510, per inspection cycle. 10 work-hours × $85 per hour = $850 ..... 150,000 The repair of the HS assembly that may be required as a result of any inspection could vary significantly from airplane to airplane. The FAA has no data to determine the costs to accomplish the repair or the number of airplanes that may require the repair. ddrumheller on DSK120RN23PROD with RULES1 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA VerDate Sep<11>2014 16:47 Dec 28, 2023 Jkt 262001 Parts cost with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Cost per product $150,850. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: E:\FR\FM\29DER1.SGM 29DER1 Federal Register / Vol. 88, No. 249 / Friday, December 29, 2023 / Rules and Regulations TABLE 1 TO PARAGRAPH (g)(1)—HS CENTRAL BOX ONE TIME INSPECTION PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2023–25–03 Piaggio Aviation S.p.A.: Amendment 39–22630; Docket No. FAA– 2023–1819; Project Identifier MCAI–2023– 00052–A. (a) Effective Date This airworthiness directive (AD) is effective February 2, 2024. (b) Affected ADs None. (c) Applicability This AD applies to Piaggio Aviation S.p.A. Model P–180 airplanes, serial numbers 1002, 1004 through 1234 inclusive, 3001 through 3012 inclusive, and 3016, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 5510, Horizontal Stabilizer Structure. (e) Unsafe Condition This AD was prompted by a report of corrosion on the various aluminum alloy reinforcements in the horizontal stabilizer (HS) central box caused by a humid environment inside the box from water ingress and/or condensation. The FAA is issuing this AD to address this condition. The unsafe condition, if not addressed, could result in reduced structural integrity of the HS and loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. ddrumheller on DSK120RN23PROD with RULES1 (g) Required Actions (1) Within the applicable compliance time specified in Table 1 to paragraph (g)(1) of this AD, do a detailed inspection of the HS central box for corrosion, in accordance with step (8), of Part A, of the Accomplishment Instructions in Piaggio Aerospace Service Bulletin 80–0489, Revision 2, dated November 30, 2022 (Piaggio SB 80–0489, Revision 2), except you are not required to record any images. VerDate Sep<11>2014 16:47 Dec 28, 2023 Jkt 262001 P–180 serial number 1002; and 1034 through 3016 inclusive. 1004 through 1033 inclusive. Compliance time (hours time-in-service (TIS) or calendar time, whichever occurs first after the effective date of this AD) Within 220 hours TIS or 13 months. Within 320 hours TIS or 13 months. (2) If, during the inspection required by paragraph (g)(1) of this AD, any corrosion is detected, before next flight, contact either the Manager, International Validation Branch, FAA; European Union Aviation Safety Agency (EASA); or Piaggio’s EASA Design Organization Approval (DOA), for an assessment of the corrosion level (level 1, 2, or 3). Note 1 to paragraph (g)(2): Appendix 1, Inspection Results Form, in Piaggio SB 80– 0489, Revision 2, may be used when contacting the FAA, EASA, or Piaggio’s EASA DOA. (3) If level 1 corrosion is found during the inspection required by paragraph (g)(1) of this AD, no further action is required by this AD. (4) If level 2 corrosion is found during the inspection required by paragraph (g)(1) of this AD, do the action in either paragraph (g)(4)(i) or (ii) of this AD. (i) Before further flight replace the HS assembly or repair the HS assembly in accordance with instructions from either the Manager, International Validation Branch, FAA; EASA; or Piaggio’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (ii) Within 400 hours TIS or 12 months, whichever occurs first after the inspection required by paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 400 hours TIS or 12 months, whichever occurs first after the most recent inspection, repeat the inspection required by paragraph (g)(1) of this AD. In addition, inspect the internal composite structure of the HS central box for surface cracks, distortion, and damage. After each repetitive inspection, before further flight, assess the inspection findings as required by paragraph (g)(2) of this AD. If it is determined that the level 2 corrosion has worsened since the last inspection; or if any surface cracks, distortion, or damage is found during any inspection; before further flight, replace the HS assembly or repair the HS assembly in accordance with instructions from either the Manager, International Validation Branch, FAA; EASA; or Piaggio’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. These inspections must be repeated at intervals not to exceed 400 hours TIS or 12 months, whichever occurs first after the most recent inspection, until a maximum of 660 hours TIS or 13 months, whichever occurs first after the inspection PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 90087 required by paragraph (g)(1) of this AD has been reached, at which time the HS assembly must be repaired or replaced. (5) If level 3 corrosion is found during the inspection required by paragraph (g)(1) of this AD, do the actions required by paragraph (g)(5)(i) or (ii) of this AD. (i) Before further flight, after the inspection required by paragraph (g)(1) of this AD, replace the HS assembly or repair the HS assembly in accordance with instructions from either the Manager, International Validation Branch, FAA; EASA; or Piaggio’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (ii) Within 200 hours TIS or 6 months, whichever occurs first after the inspection required by paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 200 hours TIS or 6 months, whichever occurs first after the most recent inspection, repeat the inspection required by paragraph (g)(1) of this AD. In addition, inspect the internal composite structure of the HS central box for surface cracks, distortion, and damage. After each repetitive inspection, before further flight, assess the inspection findings as required by paragraph (g)(2) of this AD. If it is determined that the level 3 corrosion has worsened since the last inspection; or if any surface cracks, distortion, or damage is found; before further flight, replace the HS assembly or repair the HS assembly in accordance with instructions from either the Manager, International Validation Branch, FAA; EASA; or Piaggio’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. These inspections must be repeated at intervals not to exceed 200 hours TIS or 6 months, whichever occurs first after the most recent inspection, until a maximum of 660 hours TIS or 13 months, whichever occurs first after the inspection required by paragraph (g)(1) of this AD, at which time the HS assembly must be repaired or replaced. (6) Repair or replacement of the HS assembly is terminating action for the repetitive inspections required by paragraphs (g)(4)(ii) and (g)(5)(ii) of this AD. (h) Credit for Previous Actions You may take credit for the actions required by paragraphs (g)(1) through (5) of this AD if you performed those actions before the effective date of this AD using Piaggio Aerospace Service Bulletin 80–0489, Revision 1, dated May 13, 2022. (i) Alternative Methods of Compliance (AMOCs) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, mail it E:\FR\FM\29DER1.SGM 29DER1 90088 Federal Register / Vol. 88, No. 249 / Friday, December 29, 2023 / Rules and Regulations to the address identified in paragraph (j)(2) of this AD or email to: 9-AVS-AIR730-AMOC@faa.gov. If mailing information, also submit information by email. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local Flight Standards District Office/ certificate holding district office. (j) Additional Information (1) Refer to EASA AD 2023–0007, dated January 13, 2023, for related information. This EASA AD may be found in the AD docket at regulations.gov under Docket No. FAA– 2023–1819. (2) For more information about this AD, contact Sungmo Cho, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (781) 238–7241; email: sungmo.d.cho@faa.gov. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k)(3) and (4) of this AD. ddrumheller on DSK120RN23PROD with RULES1 (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Piaggio Aerospace Service Bulletin 80–0489, Revision 2, dated November 30, 2022. (ii) [Reserved] (3) For service information identified in this AD, contact Piaggio Aviation S.p.A., P180 Customer Support, via Pionieri e Aviatori d’Italia, snc—16154 Genoa, Italy; phone: +39 331 679 74 93; email: technicalsupport@ piaggioaerospace.it. (4) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (817) 222–5110. (5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ ibr-locationsoremailfr.inspection@ nara.gov. VerDate Sep<11>2014 16:47 Dec 28, 2023 Jkt 262001 Issued on December 8, 2023. Victor Wicklund, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2023–28769 Filed 12–28–23; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–1894; Project Identifier MCAI–2022–00334–R; Amendment 39–22635; AD 2023–25–08] RIN 2120–AA64 Airworthiness Directives; Leonardo S.p.a. Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model A109E, A109S, AW109SP, A119, and AW119 MKII helicopters. This AD was prompted by multiple reports of excessive axial play on the ball bearing of the lower half of the main rotor (MR) rotating scissor assembly. This AD requires one-time scissor coupling and axial play inspections and repetitive quantitative axial play inspections and, depending on the results, additional inspections and replacing certain parts. This AD also requires reporting information and prohibits installing certain parts unless certain inspections have been accomplished. These requirements are specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 2, 2024. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 2, 2024. ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2023–1894; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the mandatory continuing airworthiness information, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room SUMMARY: PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. Material Incorporated by Reference: • For EASA material identified in this final rule, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; internet easa.europa.eu. You may find the EASA material on the EASA website at ad.easa.europa.eu. • You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110. It is also available in the AD docket at regulations.gov under Docket No. FAA– 2023–1894. Other Related Service Information: For Leonardo Helicopters service information identified in this final rule, contact Leonardo S.p.A Helicopters, Emanuele Bufano, Head of Airworthiness, Viale G. Agusta 520, 21017 C. Costa di Samarate (Va) Italy; telephone (+39) 0331–225074; fax (+39) 0031–229046; or at customerportal.leonardocompany.com/ en-US. You may also view this service information at the FAA contact information under Material Incorporated by Reference above. FOR FURTHER INFORMATION CONTACT: Jared Hyman, Aviation Safety Engineer, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; telephone (781) 238–7799; email 9-AVS-AIR-BACOCOS@faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Leonardo S.p.a. Model A109E, A109S, AW109SP, A119, and AW119 MKII helicopters. The NPRM published in the Federal Register on October 3, 2023 (88 FR 67999). The NPRM was prompted by EASA AD 2022–0037, dated March 7, 2022; corrected March 15, 2022 (EASA AD 2022–0037), issued by EASA, which is the Technical Agent for the Member States of the European Union. EASA AD 2022–0037 states that there have been multiple reports of excessive axial play on the ball bearing of the lower half of the MR rotating scissor assembly. In some cases, this resulted in dislodgement of the ball bearing from its seat. In the NPRM, the FAA proposed to require one-time MR rotating scissor coupling and axial play inspections and E:\FR\FM\29DER1.SGM 29DER1

Agencies

[Federal Register Volume 88, Number 249 (Friday, December 29, 2023)]
[Rules and Regulations]
[Pages 90085-90088]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-28769]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

========================================================================


Federal Register / Vol. 88, No. 249 / Friday, December 29, 2023 / 
Rules and Regulations

[[Page 90085]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-1819; Project Identifier MCAI-2023-00052-A; 
Amendment 39-22630; AD 2023-25-03]
RIN 2120-AA64


Airworthiness Directives; Piaggio Aviation S.p.A. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Piaggio Aviation S.p.A. (Piaggio) Model P-180 airplanes. This 
AD is prompted by a report of corrosion on the various aluminum alloy 
reinforcements in the horizontal stabilizer (HS) central box caused by 
a humid environment inside the box from water ingress and/or 
condensation. This AD requires a one-time detailed inspection of the HS 
central box for corrosion; an assessment of the corrosion level; and 
depending on the determination, repetitive detailed inspections of the 
HS central box for corrosion and the internal composite structure for 
surface cracks, distortion, and damage; and repair or replacement of 
the HS assembly. Repair or replacement of the HS assembly is 
terminating action for the repetitive inspections. The FAA is issuing 
this AD to address the unsafe condition on these products.

DATES: This AD is effective February 2, 2024.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 2, 
2024.

ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov 
under Docket No.FAA-2023-1819; or in person at Docket Operations 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this final rule, the mandatory 
continuing airworthiness information (MCAI), any comments received, and 
other information. The address for Docket Operations is U.S. Department 
of Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
    Material Incorporated by Reference:
     For service information identified in this final rule, 
contact Piaggio Aviation S.p.A., P180 Customer Support, via Pionieri e 
Aviatori d'Italia, snc--16154 Genoa, Italy; phone: +39 331 679 74 93; 
email: [email protected].
     You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 901 Locust, 
Kansas City, MO 64106. For information on the availability of this 
material at the FAA, call (817) 222-5110. It is also available at 
regulations.gov under Docket No. FAA-2023-1819.

FOR FURTHER INFORMATION CONTACT: Sungmo Cho, Aviation Safety Engineer, 
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (781) 
238-7241; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to certain serial-numbered 
Piaggio Model P-180 airplanes. The NPRM published in the Federal 
Register on September 7, 2023 (88 FR 61482). The NPRM was prompted by 
AD 2023-0007, dated January 13, 2023 (also referred to as the MCAI), 
issued by the European Union Aviation Safety Agency (EASA), which is 
the Technical Agent for the Member States of the European Union. The 
MCAI states that an occurrence of corrosion was found inside the HS 
central box of a Piaggio Model P-180 airplane during scheduled 
maintenance. A subsequent investigation and inspection of 16 other 
Piaggio Model P-180 airplanes of various configurations and ages 
revealed that corrosion of differing levels of severity was found on 
various aluminum alloy reinforcements in the HS central box of all the 
inspected airplanes. The MCAI also states that this corrosion was 
caused by the formation of a humid environment inside the HS central 
box, from water ingress and/or condensation. Further investigation 
revealed that airplanes left in prolonged inactivity or parked outside 
are more prone to develop corrosion damage.
    To address the unsafe condition, the MCAI requires a one-time 
detailed inspection of the HS central box for corrosion, contacting 
Piaggio for a determination of the corrosion level, and depending on 
that determination, repetitive detailed inspections of the HS central 
box for corrosion and the internal composite structure for surface 
cracks, distortion, and damage; and depending on the results, repair or 
replacement of the HS assembly. The MCAI states that repair or 
replacement of the HS assembly is terminating action for the repetitive 
inspections.
    In the NPRM, the FAA proposed to require a one-time detailed 
inspection of the HS central box for corrosion; an assessment of the 
corrosion level; and depending on the determination, repetitive 
detailed inspections of the HS central box for corrosion and the 
internal composite structure for surface cracks, distortion, and 
damage; and repair or replacement of the HS assembly. Repair or 
replacement of the HS assembly is terminating action for the repetitive 
inspections.
    The FAA is issuing this AD to address corrosion on the various 
aluminum alloy reinforcements in the HS central box. The unsafe 
condition, if not addressed, could result in reduced structural 
integrity of the HS, and loss of control of the airplane.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2023-1819.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from one individual commenter. The 
commenter supported the NPRM and requested a change. The following 
presents the comment received on the NPRM and the FAA's response to the 
comment.

Request To Revise Costs of Compliance Section of the NPRM

    An individual commenter requested that the FAA contact Piaggio for 
the exact price per unit of replacement

[[Page 90086]]

parts. The commenter explained that this would provide operators with a 
more accurate estimate of the NPRM's economic effect and allow 
operators to be financially prepared.
    The FAA disagrees with the commenter's request because the 
estimated cost for a replacement HS assembly provided in this final 
rule is based on a cost estimate from Piaggio. Accordingly, the FAA 
considers the cost estimates provided in this final rule to be 
sufficient and the FAA has not changed this AD regarding this issue.

Conclusion

    These products have been approved by the aviation authority of 
another country and are approved for operation in the United States. 
Pursuant to the FAA's bilateral agreement with this State of Design 
Authority, it has notified the FAA of the unsafe condition described in 
the MCAI referenced above. The FAA reviewed the relevant data, 
considered the comment received, and determined that air safety 
requires adopting this AD as proposed. Accordingly, the FAA is issuing 
this AD to address the unsafe condition on these products. This AD is 
adopted as proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Piaggio Aerospace Service Bulletin 80-0489, 
Revision 2, dated November 30, 2022 (Piaggio SB 80-0489, Revision 2). 
This service information specifies procedures for a one-time detailed 
inspection of the HS central box for corrosion, a report of the 
inspection results to Piaggio for a determination of the corrosion 
level, repetitive inspections of the HS central box as needed, and 
applicable corrective actions. The corrective actions include 
installation of a serviceable HS assembly, which is terminating action 
for the repetitive inspections.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in ADDRESSES.

Differences Between This AD and the MCAI

    The MCAI requires contacting the manufacturer for a determination 
of the corrosion level if any corrosion is found during the initial 
inspection of the HS central box, and if it is determined that level 2 
or 3 corrosion is present, having the manufacturer provide the 
threshold and intervals for doing repetitive inspections of the HS 
central box. This AD requires contacting either the FAA, EASA, or 
Piaggio's EASA Design Organization Approval (DOA). If approved by the 
DOA, the approval must include the DOA-authorized signature.
    Although Piaggio SB 80-0489, Revision 2, specifies to record the 
image of the location of corroded areas, this AD does not require that 
action.

Costs of Compliance

    The FAA estimates that this AD affects 102 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                 Action                          Labor cost           Parts cost      product       operators
----------------------------------------------------------------------------------------------------------------
Initial inspection of HS central box     6 work-hours x $85 per               $0          $510          $52,020
 for corrosion.                           hour = $510.
----------------------------------------------------------------------------------------------------------------


                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                  Action                            Labor cost           Parts cost        Cost per product
----------------------------------------------------------------------------------------------------------------
Repetitive inspections of HS central box   6 work-hours x $85 per hour           $0  $510, per inspection cycle.
 for corrosion.                             = $510, per inspection
                                            cycle.
Repetitive inspections for surface         6 work-hours x $85 per hour            0  $510, per inspection cycle.
 cracks, distortion, and damage.            = $510.
Replace HS assembly......................  10 work-hours x $85 per          150,000  $150,850.
                                            hour = $850.
----------------------------------------------------------------------------------------------------------------

    The repair of the HS assembly that may be required as a result of 
any inspection could vary significantly from airplane to airplane. The 
FAA has no data to determine the costs to accomplish the repair or the 
number of airplanes that may require the repair.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

[[Page 90087]]

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2023-25-03 Piaggio Aviation S.p.A.:
    Amendment 39-22630; Docket No. FAA-2023-1819; Project Identifier 
MCAI-2023-00052-A.

(a) Effective Date

    This airworthiness directive (AD) is effective February 2, 2024.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Piaggio Aviation S.p.A. Model P-180 
airplanes, serial numbers 1002, 1004 through 1234 inclusive, 3001 
through 3012 inclusive, and 3016, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC) Code 5510, Horizontal 
Stabilizer Structure.

(e) Unsafe Condition

    This AD was prompted by a report of corrosion on the various 
aluminum alloy reinforcements in the horizontal stabilizer (HS) 
central box caused by a humid environment inside the box from water 
ingress and/or condensation. The FAA is issuing this AD to address 
this condition. The unsafe condition, if not addressed, could result 
in reduced structural integrity of the HS and loss of control of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) Within the applicable compliance time specified in Table 1 
to paragraph (g)(1) of this AD, do a detailed inspection of the HS 
central box for corrosion, in accordance with step (8), of Part A, 
of the Accomplishment Instructions in Piaggio Aerospace Service 
Bulletin 80-0489, Revision 2, dated November 30, 2022 (Piaggio SB 
80-0489, Revision 2), except you are not required to record any 
images.

     Table 1 to Paragraph (g)(1)--HS Central Box One Time Inspection
------------------------------------------------------------------------
                                         Compliance time (hours time-in-
                                         service (TIS) or calendar time,
          P-180 serial number              whichever occurs first after
                                          the effective date of this AD)
------------------------------------------------------------------------
1002; and 1034 through 3016 inclusive..  Within 220 hours TIS or 13
                                          months.
1004 through 1033 inclusive............  Within 320 hours TIS or 13
                                          months.
------------------------------------------------------------------------

    (2) If, during the inspection required by paragraph (g)(1) of 
this AD, any corrosion is detected, before next flight, contact 
either the Manager, International Validation Branch, FAA; European 
Union Aviation Safety Agency (EASA); or Piaggio's EASA Design 
Organization Approval (DOA), for an assessment of the corrosion 
level (level 1, 2, or 3).

    Note 1 to paragraph (g)(2):
    Appendix 1, Inspection Results Form, in Piaggio SB 80-0489, 
Revision 2, may be used when contacting the FAA, EASA, or Piaggio's 
EASA DOA.

    (3) If level 1 corrosion is found during the inspection required 
by paragraph (g)(1) of this AD, no further action is required by 
this AD.
    (4) If level 2 corrosion is found during the inspection required 
by paragraph (g)(1) of this AD, do the action in either paragraph 
(g)(4)(i) or (ii) of this AD.
    (i) Before further flight replace the HS assembly or repair the 
HS assembly in accordance with instructions from either the Manager, 
International Validation Branch, FAA; EASA; or Piaggio's EASA DOA. 
If approved by the DOA, the approval must include the DOA-authorized 
signature.
    (ii) Within 400 hours TIS or 12 months, whichever occurs first 
after the inspection required by paragraph (g)(1) of this AD, and 
thereafter at intervals not to exceed 400 hours TIS or 12 months, 
whichever occurs first after the most recent inspection, repeat the 
inspection required by paragraph (g)(1) of this AD. In addition, 
inspect the internal composite structure of the HS central box for 
surface cracks, distortion, and damage. After each repetitive 
inspection, before further flight, assess the inspection findings as 
required by paragraph (g)(2) of this AD. If it is determined that 
the level 2 corrosion has worsened since the last inspection; or if 
any surface cracks, distortion, or damage is found during any 
inspection; before further flight, replace the HS assembly or repair 
the HS assembly in accordance with instructions from either the 
Manager, International Validation Branch, FAA; EASA; or Piaggio's 
EASA DOA. If approved by the DOA, the approval must include the DOA-
authorized signature. These inspections must be repeated at 
intervals not to exceed 400 hours TIS or 12 months, whichever occurs 
first after the most recent inspection, until a maximum of 660 hours 
TIS or 13 months, whichever occurs first after the inspection 
required by paragraph (g)(1) of this AD has been reached, at which 
time the HS assembly must be repaired or replaced.
    (5) If level 3 corrosion is found during the inspection required 
by paragraph (g)(1) of this AD, do the actions required by paragraph 
(g)(5)(i) or (ii) of this AD.
    (i) Before further flight, after the inspection required by 
paragraph (g)(1) of this AD, replace the HS assembly or repair the 
HS assembly in accordance with instructions from either the Manager, 
International Validation Branch, FAA; EASA; or Piaggio's EASA DOA. 
If approved by the DOA, the approval must include the DOA-authorized 
signature.
    (ii) Within 200 hours TIS or 6 months, whichever occurs first 
after the inspection required by paragraph (g)(1) of this AD, and 
thereafter at intervals not to exceed 200 hours TIS or 6 months, 
whichever occurs first after the most recent inspection, repeat the 
inspection required by paragraph (g)(1) of this AD. In addition, 
inspect the internal composite structure of the HS central box for 
surface cracks, distortion, and damage. After each repetitive 
inspection, before further flight, assess the inspection findings as 
required by paragraph (g)(2) of this AD. If it is determined that 
the level 3 corrosion has worsened since the last inspection; or if 
any surface cracks, distortion, or damage is found; before further 
flight, replace the HS assembly or repair the HS assembly in 
accordance with instructions from either the Manager, International 
Validation Branch, FAA; EASA; or Piaggio's EASA DOA. If approved by 
the DOA, the approval must include the DOA-authorized signature. 
These inspections must be repeated at intervals not to exceed 200 
hours TIS or 6 months, whichever occurs first after the most recent 
inspection, until a maximum of 660 hours TIS or 13 months, whichever 
occurs first after the inspection required by paragraph (g)(1) of 
this AD, at which time the HS assembly must be repaired or replaced.
    (6) Repair or replacement of the HS assembly is terminating 
action for the repetitive inspections required by paragraphs 
(g)(4)(ii) and (g)(5)(ii) of this AD.

(h) Credit for Previous Actions

    You may take credit for the actions required by paragraphs (g)(1) 
through (5) of this AD if you performed those actions before the 
effective date of this AD using Piaggio Aerospace Service Bulletin 80-
0489, Revision 1, dated May 13, 2022.

(i) Alternative Methods of Compliance (AMOCs)

    The Manager, International Validation Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send 
your request to your principal inspector or local Flight Standards 
District Office, as appropriate. If sending information directly to the 
manager of the International Validation Branch, mail it

[[Page 90088]]

to the address identified in paragraph (j)(2) of this AD or email to: 
[email protected]. If mailing information, also submit 
information by email. Before using any approved AMOC, notify your 
appropriate principal inspector, or lacking a principal inspector, the 
manager of the local Flight Standards District Office/certificate 
holding district office.

(j) Additional Information

    (1) Refer to EASA AD 2023-0007, dated January 13, 2023, for related 
information. This EASA AD may be found in the AD docket at 
regulations.gov under Docket No. FAA-2023-1819.
    (2) For more information about this AD, contact Sungmo Cho, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: (781) 238-7241; email: [email protected].
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (k)(3) and (4) of this AD.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the incorporation 
by reference of the service information listed in this paragraph under 
5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do the 
actions required by this AD, unless the AD specifies otherwise.
    (i) Piaggio Aerospace Service Bulletin 80-0489, Revision 2, dated 
November 30, 2022.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact Piaggio 
Aviation S.p.A., P180 Customer Support, via Pionieri e Aviatori 
d'Italia, snc--16154 Genoa, Italy; phone: +39 331 679 74 93; email: 
[email protected].
    (4) You may view this service information at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 901 Locust, Kansas City, 
MO 64106. For information on the availability of this material at the 
FAA, call (817) 222-5110.
    (5) You may view this material at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, visit www.archives.gov/federal-register/cfr/[email protected]">www.archives.gov/federal-register/cfr/[email protected].

    Issued on December 8, 2023.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2023-28769 Filed 12-28-23; 8:45 am]
BILLING CODE 4910-13-P
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